TCDS A45EU

Page No. 1 2 3 4 5 6 7 8 9 Rev. No. 3 1 1 1 1 1 1 1 2 Surrendered October 27, 2009 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A45EU Revision 3 BAe/SNIAS Concorde Type 1 November 24, 2009 TYPE CERTIFICATE DATA SHEET NO. A45EU . This data sheet, which is a part of Type Certificate No. A45EU prescribes conditions and limitations under which the aircraft for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder BRITISH AEROSPACE and SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (1) This TC was surrendered for cancellation on October 27, 2009. Only standard airworthiness certificates issued prior to October 27, 2009 are valid. (2) Future unsafe conditions existing in the aircraft may result in the revocation of the airworthiness certificates of the aircraft if there is no entity to comply with 14 CFR § 21.99(a), “Required design changes.” (3) Replacement parts may not be available in the future. I - CONCORDE Type 1 (Transport Category Supersonic Airplane), approved January 9, 1979 Engines: 4 - Rolls-Royce/SNECMA Olympus Mk 610-14-28 engines, incorporating Type A6A16/24AL or Type A6A16/24CA control amplifiers. Fuel: (a) Engine fuels to the following specifications are approved for unlimited use. (For fuels approved for limited use, refer to the approved Concorde Airplane Flight Manual). 1. ASTM D 1655-75 Grades JET A1 2. French specification AIR 3405 C Issue 4 3. British specification D.Eng.RD 2494 Issue 7 Amdt 3 and 2453 Issue 3 Amdt 3 4. Canadian specification 3-GP-23h (b) The following additive must be used in engine fuels SHELL ASA 3 antistatic additive, in concentration not exceeding 1.0 mg/liter (0.4 lb per 50,000 US Gallons). (c) The following additives maybe used in engine fuels: 1. Anti-icing additive to specifications MIL-1-27686 E, D.Eng.RD.2451 Issue 2, or AIR 3652 A, at a concentration not in excess of 0.15 percent by volume. 2. Corrosion inhibitors HITEC E 515 or TOLAD 245, in concentration not exceeding, respectively, 21 mg/liter (8.9 lb. per 50,000 US Gallons and 34 mg/liter (14.3 lb. per 50,000 US Gallons). A45EU Page 2 of 9 3. Automate Yellow 662 or 662 F fuel dye may be added at concentrations not exceeding 120 mg/liter (50 lb. per 50,000 US Gallons). This additive should be used only when necessary to check for fuel system leakage. 4. Fluid AL 38, a combination of anti-icing additive and corrosion inhibitor HITEC E 515.AL 38, may be added at concentrations not exceeding 0.13 percent by volume providing that the basic fuel does not contain either HITEC E 515 or anti-icing additive. Oil: The following oils are approved for the OLYMPUS engines: BP ENER JET 523 ESSO ETO 25 MOBIL RM 193 A-3 SHELL ASTO 555 The following oils are approved for the Integrated Drive Generator: ESSO ETO 25 ESSO ENCO 2380 Engine Limits: Condition Static Thrust (Lbs) SL - ISA N1* (Low Compressor) N2* (High Compressor) ** EGT Time Limit Start and relight - - - 550°C 2 sec. ***Contingency 38,130 102% 106.8% 883°C 2.5 sec. Takeoff (with reheat) 37,080 102% 105.7% 806°C 5 min. Takeoff (without reheat) 31,350 102% 105.7% 806°C 5 min. Reheated climb 32,800 102% 105.1% 755°C 15 min. Maximum continuous 28,800 102% 105.3% 736°C Unrestricted Idle - - 60% (min) Unrestricted Maximum overspeed 108.5% 110.0% - 20 sec. Reverse (ground) - - 98.0% - 30 sec. Reverse (flight) - (as obtained at reverse idle) - 4 min. *100% N1 = 6,500 rpm; 100% N2 = 8530 rpm. **E.G.T. limitations vary with total temperature as presented in the approved Concorde Airplane Flight manual; the values shown herein are the highest authorized. ***Eligible only with unlimited-type fuels. Oil Temperature: Maximum for start of takeoff 125°C Maximum takeoff & transient (5 min.) 195°C Maximum for continuous operation 190°C Minimum for motoring cycle -40°C Minimum for starting -35°C Minimum for advance above idle -20°C Page 3 of 9 A45EU Oil Pressure: Pre-Mod 8562 Post-Mod 8562 Minimumfor continued operation 13 psi 5 psi Minimum for takeoff 18 psi 10 psi Fuel Temperature: Kerosene Type Wide-Cut Type Minimum for starting -40°C -40°C Minimum for advance above idle 20°C -40°C Maximum for continuous operation 150°C 50°C Maximum transient (2 min.) 170°C 50°C Fuel Pressure: Minimum at engine inlet 12.5 psia 20 psia Maximum fuel filter differential 7 psi 7 psi Airspeed limits (IAS): V mo/Mmo Maximum operating limit As presented in the speed and Mach number approved Concorde AFM V a Manoeuvring As presented in the approved Concorde AFM V la Lowest authorized As presented in the approved Concorde AFM V lo Landing gear operation 270 kts (M 0.7) V le Landing gear extended 270 kts (M 0.7) V Nose/visor Visor down or operating 325 kts (M 0.8) Nose 5° or operating between UP and 5° 325 kts (M 0.8) Nose DOWN or operating between 5° and DOWN 270 kts @ altitudes below 20,000 ft. V Landing lights Max. speed for extension, retraction or extended position 270 kts V mc Minimum Control Speed with the critical engine inoperative On the ground V mcg 116 kts In flight (takeoff) V mc 132 kts In flight (approach) V mcl 150 kts V Tire limit speed As presented in the approved Concorde AFM V Max. for windscreen wiper operation 325 kts V Max. for fuel jettison M = 0.93 A45EU Page 4 of 9 Miscellaneous Limitations: Maximum total temperature, Tmo 127°C Maximum positive incidence 16.5°C Maximum negative pitch attitude -5.5°C above M = 1.0 Nose position for takeoff -5°C C.G. range (Landing gear extended): FORWARD AFT Weight Landing En route Takeoff Landing En route Takeoff Above 96,000 kg (211,640 lb) 52.5% All All See All tanks full weights weights Approved except tank 11 52.5% 52.5% Airplane 54% 96,000 kg (211,640 lb) to 88,000 kg (194,010 lb) Linear variation Between 52.5% And 52% Flight Manual Below 88,000 kg (194,010 lb) 52% See Approved Airplane Flight Manual. Other conditions 53.5% Landing gear retraction moment is -1470 m.kg (-10,635 ft.lb). (Gear retraction moves C.G. forward approximately 0.03% Co.) Datum: The datum for center-of-gravity computa tions is a vertical reference plane located 8.333 feet (2.540 m) forward of Fuselage Station XA.0. A reference rigging point "C" is provided on the airframe 83.172 feet (25.351 m) aft of the datum at 13.66% C o. M.A.C.: The "reference root chord" (C o) is 90.748 feet (27.660 m) in length; its leading edge is located 70.771 feet (21.570 m) aft of the datum. Leveling Means: Clinometer on the cabin rails. Maximum Weights: Taxi weight 186,880 kg 412,000 lb (See NOTE 4) Takeoff weight 185,070 kg 408,000 lb Landing weight 111,130 kg 245,000 lb Zero fuel weight 92,080 kg 203,000 lb Minimum Crew: For all flights: Pilot, copilot and third crew member capable of performing the duties of a flight engineer (systems operator). Maximum Passengers: 128 - based on compliance with FAA emergency evacuation demonstration requirements (FAR 25.803(c)) - See approve d interior arrangement drawing for maximum passenger capacity approved for each airplane as delivered. Page 5 of 9 A45EU Maximum Baggage: Total Running Load Limit Floor Strength Limit Under floor hold 995 kg 320 kg/m 488 kg/m 2 Forward of door (2,194 lb) (210 lb/ft) (100 lb/ft 2) Aft of door 585 kg (1,290 lb) Rear hold 2,767 kg 670 kg/m 488 kg/m 2 Lashed freight (6,100 lb) (450 lb/ft) (100 lb/ft 2) or Unlashed freight 2,268 kg (5,000 lb) Fuel Capacity: Fuel tank capacity (lb) - (At density of 6.68 lb/US Gallon). Tank No. Usable Weight Total Weight Arm (% MAC) 1 9,348 9,361 39.80 2 10,176 10,207 76.10 3 10,176 10,207 76.10 4 9,348 9,361 39.80 5 16,032 16,072 49.40 5A 4,956 4,963 74.80 6 25,803 25,889 66.70 7 16,490 16,525 64.70 7A 4,956 4,963 74.80 8 28,590 28,645 46.70 9 24,710 24,747 16.90 10 26,597 26,618 30.50 11 23,192 23,218 113.90 Systems 827 1,021 69.43 TOTAL 211,200 211,797 56.23 Oil Capacity: Each engine: - 26 US quarts total - 11 US quarts usable - 6.5 US quarts minimum for starting Maximum Operating Altitude: 60,000 ft. Control Surface Movements: As specified in SNIAS Document No. 459.000/75. A45EU Page 6 of 9 Serial Numbers Eligible: S/N 1 through S/N 16. A French "Certificat de Navigabilite pour Exportation", or a British "Certificate of Airworthiness for Export", endorsed as noted under "Import Requirements", must be submitted for each individual ai rcraft for which application for US certification is made. The type design approved under this Type Certificate is defined in Concorde Document No. 408.106/78, Issue 2, including Revision 1 and later revisions. Additional modifications generated by Air France or by British Airways, and approved by DGAC or CAA, as appropriate, are defined in the following: (1) Air France Document No. AF-01-TSS, "Index of Air France - originated modifications approved in compliance with FAA and DGAC regulations". (2) Civil Aviation Authority le tter 9/30/CON 10FH, dated December 15, 1978. Import Requirements: An FAA Standard Airworthiness Certificate may be issued on the basis of a French "Certificat de Navigabilite pour Exportation" signed by a representative of the Direction Generale de l'Aviation Civile (DGAC), of France, or a British "Certificate of Airworthiness for Export" signed by a representative of the Civil Aviation Authority (CAA) of the United Kingdom, containing the following or equivalent statement: "The airplane covered by this certificate has been examined, tested and found to conform to the type design approved under Type Certificate No. A45EU and to be in condition for safe operation". In order for the FAA to make the finding that a Concorde Type 1 aircraft is in a condition for safe operation, the FAA certificating inspector or other authorized person must contact the Manager, International Branch, ANM-116, FAA Transport Airplane Directorate; 1601 Lind Avenue Southwest; Renton, Washington 98055; telephone (425) 227-2196; fax (425) 227-1149, prior to issuance of the U.S. airworthiness certificate to obtain the FAA Required Modification List (RML) for the Concorde. Compliance with the one time modifications identified in the RML for the Concorde is required in the interest of safety and is necessary for a Concorde aircraft to be found in a condition for safe operation. Certification basis: FAR 21.29(a)(1)(ii) based upon: The Anglo/French Supersonic Transport TSS Standards, as defined in Contents List No. 29, dated March 26, 1976. Portions of FAR 25 effective February 1, 1965, including Amendment Nos. 25-1 through 25-17, plus Amendment No. 25-18 with respect to new FAR 25.1001(i), and Amendment Nos. 25-22 and 25-24 with respect to new FAR 25.1303(b)(4), as determined to be applicable through code comparison of FAR 25 and TSS Standards. Page 7 of 9 A45EU Portions of US Special Conditions for Concorde, No. 25-43-EU-12, dated June 21, 1972, including Amendment Nos. 1 through 5, determined to be applicable through code comparison of those Special Conditions and TSS Standards. FAR Part 36, dated December 1, 1969, including Amendment Nos. 1 through 10. Equivalent safety shown in lieu of direct compliance with respect to those requirements listed in Attachment "F" of FAA Concorde Validation Program No. A45EU. The aircraft is approved with respect to optional certification requirements relating to ditching, ditching equipment and ice protection, corresponding to FAR 25.801, 25.1415 and 25.1419, respectively. Date of Application : July 15, 1965. Type Certificate No. A45EU, issued January 9, 1979. Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for airworthiness certification. Concorde Equipment List SB/8/00/0020 identifies all required equipment and all optional equipment approved by the Direction Generale de l'Aviation Civile (DGAC) of France and by the Civil Aviation Authority (CAA) of the United Kingdom. In addition, the following apply: (1) CAA/DGAC-Approved Airplane Flight Manual, Document No. CSD/FM/FAA No. 1, approved December 5, 1978, is applicable for all serial numbers. (2) Rain repellant installation is required in accordance with Concorde Dwg E81/-5221. (3) Main and nose-wheel tires are required in accordance with Concorde Specification No. 459579/77. Service information: A. General: All Concorde Service Bulletins are approved by the French DGAC and the United Kingdom CAA and carry a statement to that effect. This statement may be interpreted as "FAA-approved". All Service Bulletins that are declared Mandatory by the CAA or are the subject of a French "Consigne de Navigabilite" carry a statement to that effect. Other available service documents for the Concorde include: (1) Structural Repair Manual (2) Illustrated Parts Catalog (3) Wiring Diagram Manual (4) Maintenance Manual A45EU Page 8 of 9 B. Special Maintenance Requirements: All Concorde aircraft must be maintained in accordance with a program which includes the maintenance tasks presented in the current issues of the following: (1) Concorde Document SST/B83/7013 "Special Maintenance Tasks Required for FAA Certification" (2) Concorde Service Bulletin No. 27.040 "SERVO-CONTROL INSPECTION FOR DETECTION OF CRACKS ON VARIOUS CRITICAL COMPONENTS" (3) Concorde Service Bulletin No. 27.041 "INSPECTION FOR HYDRAULIC FLUID TRANSFER DUE TO CRACKS AT SERVO- CONTROLS and (4) Concorde Service Bulletin No. 53.045 "INSPECTION OF UPPER FUSELAGE (ROOF) BETWEEN FR 41 AND FR 72" C. Special Modification Requirements: The special maintenance requirements of Subsection B above result from certification safety analyses and are necessary for compliance with the airworthiness objectives of the Concorde certification basis. Any modification to a system or component that is the subject of such maintenance requirements must be evaluated with respect to reliability in a manner consistent with the Concorde's certification safety analyses, and the airplane's maintenance program must be amended as necessary to ensure the declared level of reliability in service for the modified system or component. NOTES: NOTE 1: (a) Current weight and balance report, including list of equipment included in certificated empty weight, and loading instructions, must be in each aircraft at the time of original certification and at all times thereafter except in the case of operators having an approved weight control system. SNIAS/BAC Report "Weight and Balance Manual" contains loading information for each airplane and interior arrangement configuration as delivered. This report contains, or refers to, information relative to location of all passengers and crew member seats, location and capacity of all cargo and baggage compartments, buffets, storage spaces and coat rooms, location and capacity of lounges and lavatories. (b) The airplane must be loaded so that the C.G. is within the specified limits at all times, considering fuel loading, usage and management, gear retraction, and movement of crew and passengers from their assigned positions. Page 9 of 9 A45EU (c) The weights of unusable fuel, systems oil and hydraulic fluid must be included in the airplane operating weight empty, and are as listed below. (i) The unusable fuel is the difference between the total fuel and the usable fuel. It corresponds to that amount of fuel in the tanks and in the system determined to be unavailable to the engine in accordance with FAR 25.959. system unusable fuel: 88 kg (194 lb) arm 61.17% C o tanks unusable fuel: 183 kg (403 lb) arm 59.23% C o (In the level attitude, 660 kg (1455 lb) of fuel at 65.19% Co are undrainable). (ii) The system oil is the total amount of oil in the engine and constant speed drive units, lines and tanks: engine oil: 100 kg (220 lb) arm 76.43% C o Constant speed drive oil: 36 kg ( 79 lb) arm 78.92% C o (iii) The hydraulic fluid is the total amount of fluid in the reservoirs, lines and equipment: hydraulic fluid: 316 kg (697 lb) arm 64.69% C o NOTE 2. Placards: Required placards are illustrated in Concorde Doc. No. B10/DWR/2490, and must be installed in the designated locations. NOTE 3. Life Limitations: Concorde airplane components and equipment which are life limited are the subjects of Concorde Service Bulletins in the 900-series, identified under the appropriate ATA chapter affected. Such components and equipment must be replaced prior to expiration of the service life limit specific therein. NOTE 4. Noise-limited Takeoff Weight: For compliance with US environmental regulations, takeoff operations from US airports are limited to gross weights not greater than 181,440 kg (400,000 lb.) NOTE 5. SFAR 88 A FAA Certificate of Airworthiness is not to be issued until compliance is found to SFAR 88. …..END…..